An injection system based on two-component liquid fuel mixing reaction

Abstract

The invention discloses an injection system based on the mixed reaction of two-component liquid fuels, which relates to the technical field of scramjets, and includes an injection panel group, a first fuel control system and a second fuel control system. Connected with the first fuel control system and the second fuel control system; the injection panel group is configured so that the first liquid fuel and the second liquid fuel injected into the injection can be quickly mixed and reacted efficiently, and the first liquid fuel and the second liquid fuel can be mixed at the same time. The high heat released after the reaction of the two liquid fuels and the generated intermediate active substances are injected into the combustion chamber to realize the ignition reaction of the scramjet when flying under the condition of low Mach number (Mach number < 4.0); the first liquid fuel is The boron-containing complex, the second liquid fuel is an unsaturated hydrocarbon. The system of the invention is simple in structure, safe and efficient, and solves the problem that the scramjet engine is not easy to catch fire under the condition of low Mach number.

Description

technical field

[0001] The invention relates to the technical field of scramjets, in particular to an injection system based on the mixed reaction of two-component liquid fuels. Background technique

[0002] A scramjet is a ramjet in which fuel is burned in a supersonic airflow. When using hydrocarbon fuel, the flight Mach number of the scramjet is below 8. Because the scramjet works in the supersonic airflow, it can obtain oxygen from the atmosphere during the climbing process and give up carrying the oxidant. It has the advantages of simple structure, light weight and low cost.

[0003] However, it cannot start by itself in a static state, and it must be pushed to a certain speed by a boosting method before it can work effectively, and its low-speed performance is not good. Especially in scramjet combustion chambers flying at low Mach numbers (Mach number < 4.0), reliable ignition and efficient combustion of hydrocarbon fuels remains a challenge. The total temperatur...

Examples

Embodiment Construction

[0034] The following describes several preferred embodiments of the present invention with reference to the accompanying drawings, so as to make its technical content clearer and easier to understand. The present invention can be embodied in many different forms of embodiments, and the protection scope of the present invention is not limited to the embodiments mentioned herein.

[0035] In the drawings, structurally identical components are denoted by the same numerals, and structurally or functionally similar components are denoted by like numerals throughout. The size and thickness of each component shown in the drawings are arbitrarily shown, and the present invention does not limit the size and thickness of each component. In order to make the illustration clearer, the thicknesses of components are appropriately exaggerated in some places in the drawings.

[0036] like figure 1 As shown, the injection system based on the mixed reaction of two-component liquid fuel in the...

technical field

[0001] The invention relates to the technical field of scramjets, in particular to an injection system based on the mixed reaction of two-component liquid fuels. Background technique

[0002] A scramjet is a ramjet in which fuel is burned in a supersonic airflow. When using hydrocarbon fuel, the flight Mach number of the scramjet is below 8. Because the scramjet works in the supersonic airflow, it can obtain oxygen from the atmosphere during the climbing process and give up carrying the oxidant. It has the advantages of simple structure, light weight and low cost.

[0003] However, it cannot start by itself in a static state, and it must be pushed to a certain speed by a boosting method before it can work effectively, and its low-speed performance is not good. Especially in scramjet combustion chambers flying at low Mach numbers (Mach number < 4.0), reliable ignition and efficient combustion of hydrocarbon fuels remains a challenge. The total temperatur...

Examples

Embodiment Construction

[0034] The following describes several preferred embodiments of the present invention with reference to the accompanying drawings, so as to make its technical content clearer and easier to understand. The present invention can be embodied in many different forms of embodiments, and the protection scope of the present invention is not limited to the embodiments mentioned herein.

[0035] In the drawings, structurally identical components are denoted by the same numerals, and structurally or functionally similar components are denoted by like numerals throughout. The size and thickness of each component shown in the drawings are arbitrarily shown, and the present invention does not limit the size and thickness of each component. In order to make the illustration clearer, the thicknesses of components are appropriately exaggerated in some places in the drawings.

[0036] like figure 1 As shown, the injection system based on the mixed reaction of two-component liquid fuel in the...

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